Airworthiness Directive · Amendment 39-18233 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 737-300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014.
We are superseding Airworthiness Directive (AD) 2011-08-51 for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2011-08-51 required repetitive inspections of the lap joint at certain stringers along the entire length from certain body stations. This new AD expands the inspection area, requires additional inspections for cracks and open pockets, requires corrective actions if necessary, and revises the compliance times. This AD was prompted by an evaluation by the design approval holder (DAH) that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane.
At the applicable time specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: Do an external eddy current inspection, or internal eddy current and detailed inspections, for crack indications at stringers S-4R and S-4L, from BS 360 to BS 908, as applicable, except as provided by paragraph (h) of this AD, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Repeat the inspection(s) thereafter at the applicable intervals specified in table 1 or table 2, as applicable, of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Either inspection option may be used at any repetitive inspection cycle.
At the applicable time specified in table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD: Do one-time internal detailed and eddy current inspections for cracks at stringers S-4R and S-4L, from BS 360 to BS 908, as applicable, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Accomplishment of the inspections required by this paragraph does not terminate the repetitive inspections required by paragraph (g) of this AD.
For airplanes identified as Group 2, 3, 5, and 7 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in table 4 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do one-time internal detailed and eddy current inspections for cracks at stringer S-4R, from BS 908 to BS 1016, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014.
For airplanes identified as Group 2, 3, 5, and 7 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in table 5 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do external eddy current inspections, or internal eddy current and detailed inspections, for cracks at stringer S-4R, from BS 908 to BS 1016, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Repeat the inspection(s) thereafter at the applicable intervals specified in table 5 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. Either inspection option may be used at any repetitive inspection cycle.
For airplanes identified as Group 1, 4, and 6 in Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in table 6 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do a general visual inspection for open pockets of the lower skin panel at stringer S-4R, from BS 908 to BS 1016, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014. If any open pocket is found, before further flight, inspect or repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD.
If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Accomplishment of repairs approved in accordance with the procedures specified in paragraph (o) of this AD terminates the repetitive inspections specified in paragraphs (g) and (j) of this AD in the repaired areas only.
Where Boeing Alert Service Bulletin 737-53A1319, Revision 2, dated April 4, 2014, specifies a compliance time “after the Revision 2 date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
